The following is an aerostructural shape optimization case for the MACH tutorial wing in subsonic conditions.
Case: Wing aerostructural optimization Geometry: MACH tutorial wing Objective function: Drag coefficient (CD) Lift coefficient (CL): 0.5 Design variables: 96 FFD points moving in the y direction, seven twists, and one angle of attack. Constraints: volume, thickness, LE/TE, lift, and stress constraints (total number: 118) Mach number: ~0.3 (100 m/s) Reynolds number: ~30 million Mesh cells: ~38,000 Solver: DARhoSimpleFoam
Fig. 1. Mesh and FFD points for the MACH tutorial wing.
To run this case, first download tutorials and untar it. Then go to tutorials-main/MACH_Tutorial_Wing and run the “preProcessing.sh” script to generate the mesh:
The above script will generate a structured hex mesh using pyHyp. Then, use the following command to run the optimization with 8 CPU cores:
mpirun -np 8 python runScript_AeroStruct.py 2>&1 | tee logOpt.txt